中文摘要：

针对当前巡航导弹导航技术的不足,提出一种利用地磁场信息实现导航的方法。采用国际地磁参考场作为地磁场模型,以地磁场矢量和飞行高度值作为观测值,结合导弹的运动模型和地磁场模型,设计了无迹卡尔曼滤波算法。应用可观测矩阵和奇异值分解方法对导航系统的可观测性和可观测度做了详细分析。利用设计的导航滤波器对巡航导弹的位置和速度估计做了数学仿真。仿真结果表明了采用高阶地磁场模型比低阶地磁场模型具有更好的导航精度;同时观测噪声强度越小,则导航精度越高。该方法具有较好的滤波收敛性、稳定性和适中的导航精度,可用于巡航导弹初、中制导段的自主导航。

英文摘要：

In order to overcome the deficiencies of current navigation technologies of cruise missile, a navigation method using geomagnetic field information was presented. A navigation filter based on the unscented Kalman filter algorithm was designed by taking the international geomagnetic reference field as the geomagnetic field model, the geomagnetic field vectors and the flight height as observed variables, and combining the missile motion model with the geomagnetic field model. The observability and observable degree of the navigation system were analyzed in detail by the observability matrix and the singular value decomposition method. The location and speed of cruise missile were simulated by the navigation filter. The simulated results show that the navigation precision with high order geomagnetic field model is better than that with low order geomagnetic field model; the smaller the observed noise intensity is, the higher the navigation precision is. The method provides better filter convergence, stability and moderate navigation precision for autonomous navigation in the initial and midcourse phase guidances of cruise missile.